Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(goe439-il) GOE 439 AIRFOIL | Gottingen 439 airfoil Max thickness 7.9% at 30% chord Max camber 5.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe359-il) GOE 359 AIRFOIL | Gottingen 359 airfoil Max thickness 7.8% at 30% chord Max camber 5.8% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe369-il) GOE 369 AIRFOIL | Gottingen 369 airfoil Max thickness 5.9% at 30% chord Max camber 5.4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe439-il,goe359-il,goe369-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe439-il | 50,000 | 9 | 28.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe439-il | 50,000 | 5 | 40.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe439-il | 100,000 | 9 | 59.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe439-il | 100,000 | 5 | 61.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe439-il | 200,000 | 9 | 79.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe439-il | 200,000 | 5 | 80.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe439-il | 500,000 | 9 | 108.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe439-il | 500,000 | 5 | 106.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe439-il | 1,000,000 | 9 | 129.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe439-il | 1,000,000 | 5 | 123.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe359-il | 50,000 | 9 | 35.9 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe359-il | 50,000 | 5 | 41.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe359-il | 100,000 | 9 | 61.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe359-il | 100,000 | 5 | 63 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe359-il | 200,000 | 9 | 83.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe359-il | 200,000 | 5 | 82 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe359-il | 500,000 | 9 | 110.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe359-il | 500,000 | 5 | 103.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe359-il | 1,000,000 | 9 | 130.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe359-il | 1,000,000 | 5 | 103.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe369-il | 50,000 | 9 | 37.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe369-il | 50,000 | 5 | 43.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe369-il | 100,000 | 9 | 59.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe369-il | 100,000 | 5 | 63.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe369-il | 200,000 | 9 | 80.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe369-il | 200,000 | 5 | 83 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe369-il | 500,000 | 9 | 105.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe369-il | 500,000 | 5 | 94.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe369-il | 1,000,000 | 9 | 121.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe369-il | 1,000,000 | 5 | 112.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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